Aeroplane



1. E. PEARSON.

AEROPLANE.

APPLICATION FILED FEB. 13, 1920.

1,378,895. Patented May 24,1921.

2 SHEETSSHEET 1- INVENTOR ATTORNHS J/E. PEARSON.

. AEROPLANE.

APPLlCATlON FILED FEB. 13, 1920 l ,378,895.- Patented y24,1921.

2 SHEETS-SHEET 2- ATTORNEYS alga/4901;

planes P and UNITED STATES PATENT OFFICE.

- JOHN ELLIS rmnson, or MIMOSA, NORTH canonnm.

' AEROPLANE.

aeroplanes heretofore proposed without increasing the weight ofthe machine.

I will describe one form of aeroplane embodying my invention and will then point out the novel features thereof in claims.

In the accompanying drawings:

Figure 1 is a view showing in side elevation one form of aeroplane embodying my invention. I

Fig. 2 is a central longitudinal sectional view of the aeroplane shown in Fig. 1.

Fig. 3 is a transverse sectional view taken on the line 3-3 of Fig. 2.

Fig. 4' is a fragmentary detail view showing in side elevation the driving means and supporting means for one" of the propellers of the aeroplane shown in the preceding views.

Fig. 5 is an enlarged detail View of the mechanism for controlling and actuating the rudder of the aeroplane.

Similar reference characters refer to similar parts in each of the several views.

Referring specifically to the drawings F designates a fuselage upon which are supported a vertically disposed plane P and a pair of super osed horizontally disposed The fuselage is supported upon achassis comprising a forward carriage C and a-rear-carria e G each ofwhich is provided with wheels At the'rear of the planes P, P and P is a rudder R, and disposed upon opposite sides at points adjacent the opposite ends ofthe fuselage F are four propellers L, L etc. At the forward end of the fuselage F is another propeller D.

As shown in Figs-1,2 and 3, the fuselage F comprises an inner body 15 of rectangular formation in cross section and an outer body 16 of tubular formation which surrounds and is rigidly connected to the inner body. The opposite ends of the inner body 15 project beyond the ends of the outer body 16 and are tapered as indicated at '15, such end Specification of Letters Patent.

Patented May 24, 1921.

Application filed February 13, 1920. Serial No. 358,512.

portions being utilized for the storage of gasolene. Engines E are carried within the inner body 15 and are operativel connected to the several propellers L in the manner shown to advantage in Fig. 1. As

shown in Fig. 4, the propellers L, L L and L are each supported upon standards 17 secured to the outer body 16 of the fuselage. Thepropeller L is driven from its correspondlng engines through a shaft 18 WlllCll as shown inFig. 1 extends above the foward end portion 15.

As illustrated to advantage in Fig. 3, the vertical plane P consists of an upper section 19 and a lower section 20, both of which are rigidly connected tothe outer body 16 at polnts diametrically opposite to each other. As shown in Fig. 1, the sections 19 and 20 are coextensive in length with the fuselage F, the lower section 20 having its forward and rear ends inclined inwardly as shown for the purpose'of safe landing and rising of the aeroplane.

The upper horizontal plane P is partly supported upon the upper section 19 and intersects the latter at right angles as clearly shown in Fig. 3. The lower horizontal plane P is formed of two sections 21 and 22 which extend from the fuselage at diametrically opposite points and are vertical movement by guys connected to the sections and to the sections 19 and 20 of the vertical plane P, in the manner shown in Fig. 3. The horizontal planes P and P are formed in sections as shown in Fig. 2 and are maintained in spaced parallel relation to each other by struts arranged at intervals between the two. The struts are of elliptical formation in cross section as is the usual formation of such members. As shown in Fig. 2, the lower horizontal plane P is rovided at its rear end with ailerons A W ich are for the usual pur ose of preserving the side to side balance 0 the aeroplane. s shown in Fig. 2, a wlre cable K extends around the edges of the planes P and P and is connected to the outer ends of the tapered portions 15, the purpose of this arrangement being to provide the necessary reinforcement for the planes.

Referring now to Figs. 2 and 5, the rudder R is shown as comprising a direction plane 23 and an elevation plane 24: disposed at right angles to the latter and rigidly secured thereto for movement therewith.

supported against allowing of the The rudder R is movably supported upon the rear end of the fuselage F by a ball and socket joint 25 so as to allow the universal movement of the rod. The mechanism for controlling and actuating the rudder comprises in the present instance two pairs of rods 26 pivotally connected at their rear ends to the rudder and provided at their forward ends with screw threaded portions 26 upon which work worm gears 27. The worm gears 27 in turn mesh with worms 28 supported upon the opposite ends of actuat-' ing shafts 29. In thepresent instance, only one shaft 29 is shown in the drawings for actuating one pair of rods 26. Each shaft 29 is provided with a wheel 30 by means of which the shaft can be manually rotated to actuate the worms 28 which in turn rotate the worm gears 27 to effect a longitudinal movement of the rods 26 in one direction or the other according as the shaft 29 is rotated in one direction or the other. By this arrangement the rudder R can be moved to any desired position to effect the proper steering of the aeroplane.

From the foregoing description, taken in conjunction with the accompanying drawings, it will be manifest that in operation, the aeroplane is propelled with uniformity through the small L, the propeller serving to drive the aeroplane centrally along its longitudinal axis and efi'ecting in a degree an equalization of the propulsion of the other propellers. As the planes P, P and 1 are coextensive in length with the fuselage it will be manifest that an aeroplane of great rigidity is provided with a lifting surface of great area. It will also be noted, the vertical plane P serves to preserve the side to side balance of the aeroplane.

The operators of the aeroplane are housed within the inner body 15 of the fuselage.

where theyare completely protected from the elements. Access to the fuselage is gained through a door 31 as shown in Fig. 2, the forward end of the fuselage being provided with observation windows 32.

Although I have herein shown and depJropellers L, L L and scribed only one form of aeroplane embodying my invention, it is to be understood that various changes and modifications may be made .herein without departing from the spirit of the invention and the spirit and scope of the appended claims.

What I claim is:

. 1. An aeroplane comprising, a fuselage, a vertical plane comprising an upper section and a lower section arranged at diametrically opposite points on said fuselage and coextensive in length therewith, a horizontal plane comprising sections disposed at diametrically opposite points of the fuselage and coextensive in length therewith, and a second horizontal plane disposed'above the first horizontal plane and the fusela e.

2. An aeroplane comprising, a uselage including an inner body of rectangular formation and an outer body of cylindrical formation, a vertical plane arranged along the longitudinal axis of the fuselage, a hor1- zontal plane arranged along the longitudinal axis of the fuselage and. disposed at right angles to the vertical plane.

3. An aeroplane comprislng, a fuselage including an inner body of rectangular formation and an outer body of cylindricalformation, a vertical plane comprising an upper section and a lower section arranged at diametrically opposite points on the fuselage and coextensive in length therewith, a horizontal plane comprising sections disposed at diametrically opposite points in the fuselage and coextensive in length therewith, a second horizontal plane disposed above the first horizontal plane and above the fuselage, and propellers at the forward end of the fuselage and between the horizontal planes at corresponding points on the opposite sides of the fuselage.

I 4:. A fuselage foraeroplanes comprising, an inner body of angular formation, an outer body of cylindrical formation, and

conical end portions formed on the cylindrical body.

JOHN ELLIS PEARSON. 

